METHOD AND A DEVICE FOR OPTIMIZING THE UTILIZATION OF AN ENGINE

A method of optimizing the use of an aircraft power plant having at least one engine (′) operating within a performance envelope covering at least a first rating and a second rating, said first rating presenting a first power (P) usable over a predetermined first time interval (D), said second rating presenting a second power (P) greater than said first power (P), the second power (P) being usable continuously over a predetermined second time interval (D). Thus, while the engine (′) is developing a third power (P) that is both greater than the first power (P) and less than or equal to the second power (P), a potential first duration of utilization (ΔT) of continuous use of said second power (P) is determined and displayed, said first duration of utilization (ΔT) elapsing at a speed that is variable and that depends on said third power (P). 11121221131223. A method of optimizing the use of an aircraft power plant having at least one engine operating within a performance envelope covering at least a first rating and a second rating , said first rating presenting a first power (P) usable over a predetermined first time interval (D) , said second rating presenting a second power (P) greater than said first power (P) , and the second power (P) being usable continuously over a predetermined second time interval (D) , wherein while the engine ( , ′) is developing a third power (P) that is both greater than the first power (P) and less than or equal to the second power (P) , a potential first duration of utilization (ΔT) of continuous use of said second power (P) is determined and displayed , said first duration of utilization (ΔT) elapsing at a speed that is variable and that depends on said third power (P).332. A method according to claim 1 , wherein the closer the third power (P) comes to the second power (P) claim 1 , the faster the first duration of utilization (ΔT) elapses.432. A method according to claim 1 , wherein when the third power (P) is equal to the second ...

Method and Device for Optimizing the Utilization of an Engine

A method of optimizing the use of an aircraft power plant having at least one engine operating within a performance envelope covering at least a first rating and a second rating, the first rating presenting a first power (P1) usable over a predetermined first time interval (D1), the second rating presenting a second power (P2) greater than said first power (P1), the second power (P2) being usable continuously over a predetermined second time interval (D2). Thus, while the engine is developing a third power (P3) that is both greater than the first power (P1) and less than or equal to the second power (P2), a potential first duration of utilization (ΔT) of continuous use of the second power (P2) is determined and displayed, the first duration of utilization (ΔT) elapsing at a speed that is variable and that depends on said third power (P3). 1. A method of optimizing the use of an aircraft power plant having at least one engine , the method comprising:operating the engine within a performance envelope covering at least a first rating and a second rating, the first rating presenting a first power (P1) which the engine can develop over a predetermined first time interval (D1), the second rating presenting a second power (P2) greater than the first power (P1) which the engine can develop continuously over a predetermined second time interval (D2) shorter in duration than the first time interval;operating the engine to develop a third power (P3) greater than the first power (P1) and less than the second power (P2);while the engine is developing the third power (P3), determining a potential first duration of utilization (ΔT) of the engine to develop continuously the second power (P2) which takes into account engine deterioration caused while the engine is developing the third power (P3) relative to engine deterioration which would be caused if the engine developed the second power (P2) instead of the third power (P3) whereby the first duration of utilization (ΔT) is a third ...

Method of increasing the safety of a power plant, and a power plant suitable for implementing the method

The present invention relates to a method of increasing the safety of a power plant provided with at least one heat engine and a gearbox (BTP), the engine driving the gearbox (BTP), the gearbox (BTP) having a lubrication system implemented using an aqueous medium stored in a reserve, in which method a fluid comprising water is injected into the heat engine to increase the power developed by the heat engine without increasing the temperature of a member of the heat engine or to decrease the temperature without modifying the power developed by the engine, the fluid being taken from the reserve.

POWER PLANT USING TWO FUELS, INCLUDING ONE FUEL WITH A HIGH GELATION TEMPERATURE

The present invention relates to a fuel supply device for a heat engine intended for a rotary-wing aircraft, which feed device includes first and second reservoirs respectively containing first and second fuels suitable for feeding the heat engine. The second fuel is heated by passing through a heat exchanger, and then passes through a return valve positioned beyond the heat exchanger. The return valve is driven as a function of the temperature of the second fuel in order to direct the second fuel to the second reservoir when the temperature of the second fuel is lower than or equal to the setpoint temperature Tc, and to the heat engine when the temperature of the second fuel is higher than the setpoint temperature Tc. 1. A fuel supply device for a heat engine , which feed device includes two reservoirs , two feed pumps and two feed conduits , a first reservoir containing a first fuel and a second reservoir containing a second fuel , with the first and second reservoirs being in communication with a feed housing of the heat engine by means respectively of first and second feed conduits , with a first feed pump being positioned between the first reservoir and the first feed conduit and a second feed pump being positioned between the second reservoir and the second feed conduit , with the feed device also including a heat exchanger located between the second feed pump and the second feed conduit , so as to heat the second fuel before reaching the second feed conduit , as well as an outlet conduit located between the heat exchanger and the second feed conduit , and a return valve positioned between the outlet conduit and the second feed conduit and connected to a return conduit discharging into the second reservoir , with the return valve being driven as a function of the temperature of the second fuel in order to direct the second fuel to the return conduit when the temperature of the second fuel is lower than or equal to a setpoint temperature Tc , and to the second ...

METHOD OF INCREASING THE SAFETY OF A POWER PLANT, AND A POWER PLANT SUITABLE FOR IMPLEMENTING THE METHOD

The present invention relates to a method of increasing the safety of a power plant provided with at least one heat engine and a gearbox (BTP), the engine driving the gearbox (BTP), the gearbox (BTP) having a lubrication system implemented using an aqueous medium stored in a reserve, in which method a fluid comprising water is injected into the heat engine to increase the power developed by the heat engine without increasing the temperature of a member of the heat engine or to decrease the temperature without modifying the power developed by the engine, the fluid being taken from the reserve. 1. A power plant provided with at least one heat engine and with a gearbox and a reserve , the heat engine driving the gearbox , wherein the reserve is hydraulically connected via a hydraulic connection to the gearbox and to each heat engine to lubricate the gearbox and to increase the power of the heat engine without increasing its temperature or to reduce the temperature of the heat engine without reducing its power , the power plant including at least one main closure means between each heat engine and the reserve , and at least one secondary closure means between the gearbox and the reserve , the power plant including a control member for controlling the main and secondary closure means.2. A power plant according to claim 1 , wherein each main closure means comprises a main admission valve claim 1 , and each secondary closure means comprises a secondary admission valve.3. A power plant according to claim 1 , wherein claim 1 , for the gearbox including at least one member to be lubricated claim 1 , the hydraulic connection includes a duct opening out into an injection nozzle directed towards the member claim 1 , the nozzle being suitable for injecting a fluid from the reserve in the form of a jet or a mist.4. A power plant according to claim 1 , wherein for the heat engine being a turbine engine having a free turbine and a gas generator claim 1 , and for the gas generator ...

MULTI-ENGINE POWER PLANT HAVING AN EMERGENCY FLUID INJECTION SYSTEM, AND AN AIRCRAFT

A power plant () having a first and second turboshaft engines () and an emergency system () for injecting fluid into said engines (). First and second pressurization pipes () connect a tank () to each gas generator of the engines. In addition, the system () includes an injector device () for each engine, which device comprises an injector pipe () connecting said tank () to at least one injector nozzle (). A distributor () is arranged on each injector pipe (), each valve () feeding one of the engines while being connected to the gas generator of the other engine. 1. A power plant having a first turboshaft engine and a second turboshaft engine each having a gas generator , said power plant including an emergency system for injecting fluid into said engines , said system including a tank containing an aqueous fluid , wherein the power plant includes:a first pressurization pipe and a second pressurization pipe respectively connecting the tank to a first gas generator of the first engine and to a second gas generator of the second engine in order to pressurize said fluid in said tank with gas taken from each of the gas generators;one injector member per engine, each member comprising at least an injector nozzle for injecting said fluid, a first injector device having a first injector pipe connecting said tank to a first injector member of the first engine, a second injector device having a second injector pipe connecting said tank to a second injector member of the second engine; anda distributor arranged on each injector pipe, a first distributor of the first injector pipe communicating with the second pressurization pipe so that a failure of the second engine causes the first distributor to open, and a second distributor of the second injector pipe communicating with the first pressurization pipe so that the failure of the first engine causes the second distributor to open.2. A power plant according to claim 1 , wherein said tank includes an overpressure valve for ...

MULTI-ENGINE ENGINE INSTALLATION PROVIDED WITH A FLUID INJECTION AND AIRCRAFT EMERGENCY SYSTEM

La présente invention concerne une installation motrice (10) munie d'un premier turbomoteur (11) et d'un deuxième turbomoteur (16) et d'un système (20) de secours d'injection de fluide dans lesdits turbomoteurs (11, 16). Une première et une deuxième conduites de pressurisation (26, 28) relient un réservoir (21) à chaque générateur de gaz des turbomoteurs. De plus, le système (20) comporte un dispositif d'injection (35, 40) par turbomoteur comportant une conduite d'injection (36, 41) reliant ledit réservoir (21) à au moins une buse d'injection (31). Un distributeur (51, 52) est disposé le long de chaque conduite d'injection (36, 41), chaque distributeur (51) alimentant un turbomoteur étant relié au générateur de gaz de l'autre turbomoteur. The present invention relates to a power plant (10) provided with a first turbine engine (11) and a second turbine engine (16) and a backup system (20) for injecting fluid into said turbine engines (11, 16). ). A first and a second pressurization line (26, 28) connect a reservoir (21) to each gas generator of the turbine engines. In addition, the system (20) comprises an injection device (35, 40) by a turbine engine comprising an injection line (36, 41) connecting said reservoir (21) to at least one injection nozzle (31). A distributor (51, 52) is arranged along each injection line (36, 41), each distributor (51) supplying one turbine engine being connected to the gas generator of the other turbine engine.

METHOD FOR INCREASING THE SAFETY OF A MOTOR INSTALLATION, AND MOTOR INSTALLATION SUITABLE FOR CARRYING OUT SAID METHOD

MULTI-ENGINE ENGINE INSTALLATION PROVIDED WITH A FLUID INJECTION AND AIRCRAFT EMERGENCY SYSTEM

La présente invention concerne une installation motrice (10) munie d'un premier turbomoteur (11) et d'un deuxième turbomoteur (16) et d'un système (20) de secours d'injection de fluide dans lesdits turbomoteurs (11, 16). Une première et une deuxième conduites de pressurisation (26, 28) relient un réservoir (21) à chaque générateur de gaz des turbomoteurs. De plus, le système (20) comporte un dispositif d'injection (35, 40) par turbomoteur comportant une conduite d'injection (36, 41) reliant ledit réservoir (21) à au moins une buse d'injection (31). Un distributeur (51, 52) est disposé le long de chaque conduite d'injection (36, 41), chaque distributeur (51) alimentant un turbomoteur étant relié au générateur de gaz de l'autre turbomoteur. The present invention relates to a power plant (10) provided with a first turbine engine (11) and a second turbine engine (16) and a system (20) for fluid injection backup in said turbine engines (11, 16 ). First and second pressurizing lines (26, 28) connect a reservoir (21) to each gas generator of the turbine engines. In addition, the system (20) comprises a turbine engine injection device (35, 40) comprising an injection pipe (36, 41) connecting said reservoir (21) to at least one injection nozzle (31). A distributor (51, 52) is arranged along each injection line (36, 41), each distributor (51) supplying a turbine engine being connected to the gas generator of the other turbine engine.

Method and device for optimising the use of a motor

METHOD FOR INCREASING THE SAFETY OF A MOTOR INSTALLATION, AND MOTOR INSTALLATION SUITABLE FOR CARRYING OUT SAID METHOD

La présente invention concerne un procédé pour augmenter la sécurité d'une installation motrice (10) munie d'au moins un moteur thermique (1, 2) et d'une boîte de transmission de puissance (BTP), ledit moteur thermique (1, 2) entraînant ladite boîte de transmission de puissance (BTP), ladite boîte de transmission de puissance (BTP) ayant un système de lubrification réalisé à l'aide d'un moyen aqueux stocké dans un réservoir (30), au cours duquel on injecte un fluide comprenant de l'eau dans ledit moteur thermique (1, 2) pour augmenter une puissance développée par le moteur thermique (1, 2) sans augmenter la température d'un organe du moteur thermique (1, 2) ou pour diminuer ladite température sans modifier la puissance développée par le moteur thermique (1, 2) ledit fluide étant prélevé dans ledit réservoir (30). The present invention relates to a method for increasing the safety of a power plant (10) provided with at least one heat engine (1, 2) and a power transmission gearbox (BTP), said heat engine (1, 2) driving said power transmission gearbox (BTP), said power transmission gearbox (BTP) having a lubrication system made using an aqueous medium stored in a reservoir (30), during which one injects a fluid comprising water in said heat engine (1, 2) for increasing a power developed by the heat engine (1, 2) without increasing the temperature of a member of the heat engine (1, 2) or for decreasing said temperature temperature without modifying the power developed by the heat engine (1, 2) said fluid being taken from said tank (30).

METHOD AND DEVICE FOR OPTIMIZING THE USE OF A MOTOR

La présente invention concerne un procédé pour optimiser l'utilisation d'une installation motrice munie d'au moins un moteur (1, 1') certifié pour fonctionner selon au moins un premier régime et un deuxième régime, ledit premier régime présentant une première puissance (P1) utilisable selon un premier intervalle de temps (D1), ledit deuxième régime présentant une deuxième puissance (P2) supérieure à ladite première puissance (P1), la deuxième puissance (P2) étant utilisable selon un deuxième intervalle de temps (D2) en continu. Ainsi, on détermine et on affiche une première durée d'utilisation (ΔT) possible en continu de ladite deuxième puissance (P2) lorsque le moteur (1, 1') développe une troisième puissance (P3) d'une part supérieure à la première puissance (P1) et d'autre part inférieure ou égale à la deuxième puissance (P2), ladite première durée d'utilisation (ΔT) s'écoulant à une vitesse variable dépendant de ladite troisième puissance (P3). The present invention relates to a method for optimizing the use of a power plant provided with at least one engine (1, 1 ') certified to operate according to at least a first speed and a second speed, said first speed having a first power (P1) usable according to a first time interval (D1), said second speed having a second power (P2) greater than said first power (P1), the second power (P2) being usable according to a second time interval (D2) continuously. Thus, a first continuous operating time (ΔT) of said second power (P2) is determined and displayed when the motor (1, 1 ') develops a third power (P3) on the one hand greater than the first power (P1) and secondly less than or equal to the second power (P2), said first duration of use (ΔT) flowing at a variable speed dependent on said third power (P3).

MOTOR INSTALLATION USING TWO FUELS INCLUDING A FUEL WITH A HIGH TEMPERATURE OF FIGURE

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